US11378276B2 - Combustor and gas turbine - Google Patents
Combustor and gas turbine Download PDFInfo
- Publication number
- US11378276B2 US11378276B2 US16/686,678 US201916686678A US11378276B2 US 11378276 B2 US11378276 B2 US 11378276B2 US 201916686678 A US201916686678 A US 201916686678A US 11378276 B2 US11378276 B2 US 11378276B2
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- Prior art keywords
- fuel
- cavities
- combustor
- casing
- manifold
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
Definitions
- the present invention relates to a multi-stage combustor including a plurality of cavities, or manifold spaces, and a gas turbine including the same.
- a multi-stage combustor including a premix combustion burner is sometimes adopted for a low NOx-type gas turbine.
- fuel pipes for supplying a fuel to premix combustion-use nozzles, at which the fuel is ignited sequentially are connected to a fuel header through corresponding cavities, or manifold spaces, see JP-1996-135910-A and the like.
- a cavity is required for each of fuel lines, and a fuel pipe for connecting each cavity to corresponding fuel nozzles, pipes branching off from the fuel header to the respective cavities, and so on are required, resulting in a tendency for the fuel lines to become larger and complicated.
- pipe paths are lengthened to increase a waste heat loss of a fuel.
- An object of the present invention is to provide a multi-stage combustor capable of achieving a reduction in waste heat loss of a fuel with improved efficiency in arrangement of a plurality of cavities, or manifold spaces, and a gas turbine including the same.
- a multi-stage combustor includes: a combustor liner configured to define a combustion chamber therein; a plurality of fuel nozzles configured to inject a fuel into the combustion chamber; and a manifold configured to distribute the fuel to the plurality of fuel nozzles.
- the manifold is disposed on a central axis of the combustor liner.
- the manifold includes a casing, and a plurality of partitions inserted in the casing so as to be arranged in a direction of the central axis of the combustor liner to define a plurality of cavities divided by the partitions.
- the plurality of cavities are layered in the direction of the central axis of the combustor liner inside of the casing, and are connected to the corresponding fuel nozzles.
- the above embodiment of the present invention is able to achieve a reduction in waste heat loss of the fuel with improved efficiency in arrangement of the plurality of cavities.
- FIG. 1 is a diagram illustrating one example structure of a gas turbine including a combustor according to a first embodiment of the present invention
- FIG. 2 is a partial sectional view illustrating one example structure of the combustor provided in the gas turbine including the combustor according to the first embodiment of the present invention
- FIG. 3 is a diagram illustrating the combustor illustrated in FIG. 2 as viewed from a side on which a combustion chamber lies;
- FIG. 4 is a sectional view illustrating the structure of a manifold provided in the combustor according to the first embodiment of the present invention, which is a sectional view taken along line IV-IV in FIG. 3 ;
- FIG. 5 is a sectional view illustrating the structure of a manifold provided in a combustor according to a second embodiment of the present invention, which corresponds to FIG. 4 ;
- FIG. 6 is a sectional view illustrating the structure of a manifold provided in a combustor according to a third embodiment of the present invention, which corresponds to FIG. 4 .
- FIG. 1 is a diagram illustrating one example structure of a gas turbine 100 including a combustor 2 according to a first embodiment of the present invention. While the gas turbine 100 illustrated in FIG. 1 is a single-shaft gas turbine, an embodiment of the present invention is also applicable to a so-called twin-shaft gas turbine.
- the gas turbine 100 illustrated in FIG. 1 includes a compressor 1 , the combustor 2 , and a turbine 3 .
- the compressor 1 and the turbine 3 are coupled to each other through a shaft which is not depicted.
- the compressor 1 is driven to rotate by the turbine 3 , and compresses an air 6 sucked in through an air inlet portion 5 to generate a high-pressure compressed air, and supplies the high-pressure compressed air to the combustor 2 .
- the combustor 2 burns a fuel mixed with the compressed air supplied from the compressor 1 to generate a high-temperature combustion gas 7 , and supplies the high-temperature combustion gas 7 to the turbine 3 .
- the turbine 3 is driven by the combustion gas 7 supplied from the combustor 2 .
- Load equipment such as a generator or a pump, is coupled to the turbine 3 or the compressor 1 .
- the generator as the load equipment is coupled to the turbine 3
- rotational power of the turbine 3 minus power that is used to drive the compressor 1 is converted to electric power in the generator.
- the combustion gas 7 having driven the turbine 3 , is discharged to the atmosphere as turbine exhaust.
- FIG. 2 is a partial sectional view illustrating one example structure of the combustor 2 provided in the gas turbine 100 including the combustor 2 according to an embodiment of the present invention.
- FIG. 3 is a diagram illustrating the combustor 2 illustrated in FIG. 2 as viewed from a side on which a combustion chamber lies.
- the combustor 2 is of a multi-stage combustion type, is inserted in a casing 4 of the gas turbine 100 , see FIG. 1 , and includes a combustor liner 10 , an outer cylinder 20 , a burner 30 , and a manifold 40 .
- the combustor liner 10 is a cylindrical member configured to define a combustion chamber 11 therein, and is positioned on a downstream side, a right side in FIG. 2 , of the burner 30 in a fuel injection direction.
- An inside space defined by the combustor liner 10 is the combustion chamber 11 , and the fuel supplied from the burner 30 is mixed with the air in the combustion chamber 11 and is then burned to generate the combustion gas 7 .
- the outer cylinder 20 of the combustor 2 covers an outer circumference of the combustor liner 10 , and an annular space defined between the outer cylinder 20 and the combustor liner 10 forms an annular flow channel 21 that guides a compressed air A 2 from the compressor 1 to an upstream side of the burner 30 .
- the compressed air A 2 flowing into the annular flow channel 21 , convection-cools the combustor liner 10 .
- a part of the compressed air A 2 that flows in the annular flow channel 21 flows into the combustor liner 10 through a large number of cooling holes, not depicted, provided in an outer circumferential portion of the combustor liner 10 , and is used for film cooling of the combustor liner 10 .
- the rest of the compressed air A 2 which has not flown into the cooling holes, is supplied to the burner 30 through the annular flow channel 21 .
- the compressed air A 2 that has been supplied to the burner 30 is mixed with a fuel distributed from the manifold 40 and injected from a diffusion combustion-use fuel nozzle 31 a , see FIG. 3 , or premix combustion-use fuel nozzles 32 a , 32 b , and 32 c , see FIG. 4 , and the fuel is burned in the combustion chamber 11 as mentioned above.
- the burner 30 includes a diffusion burner 31 and a premix burner 32 .
- the diffusion burner 31 is a burner of a diffusion combustion type, and includes the fuel nozzle 31 a and a swirler 31 b .
- the fuel nozzle 31 a is disposed on a central axis of the combustor 2 in a central axis extending direction, includes a fuel injection hole at a tip, which is a right end in FIG. 1 , and directly injects the fuel into the combustion chamber 11 , in a rightward direction in FIG. 1 , through the fuel injection hole.
- the swirler 31 b is disposed so as to surround an outer circumference of the tip of the fuel nozzle 31 a or its vicinity, and injects a swirling air flow to enhance combustion stability of the diffusion burner 31 .
- the premix burner 32 is a burner of a premix combustion type, and includes an inner cylinder 32 d , an outer cylinder 32 e , a plurality of partitions, or premixer vanes, 32 g , and the plurality of fuel nozzles 32 a to 32 c , see FIG. 4 .
- the inner cylinder 32 d and the outer cylinder 32 e are cylindrical members that form a premixer, and the inner cylinder 32 d covers an outer circumference of the diffusion burner 31 , while the outer cylinder 32 e covers an outer circumference of the inner cylinder 32 d .
- a cylindrical space defined between the inner cylinder 32 d and the outer cylinder 32 e is connected with the annular flow channel 21 .
- the plurality of, sixteen in this example, partitions 32 g of the premix burner 32 divide the cylindrical space between the inner cylinder 32 d and the outer cylinder 32 e into a plurality of, sixteen in this example, premix chambers 32 f .
- Each premix chamber 32 f is a space in which the fuel mixes with the air.
- a ring-shaped flame stabilizer 33 is provided at exits of the premix chambers 32 f , that is, on a side of the premix burner 32 on which the combustion chamber 11 lies.
- the flame stabilizer 33 is a flame stabilizer of a physically stabilizing type disposed as an obstacle in flow channels of a premixed gas to form a circulating flow on the downstream side, i.e., in the combustion chamber 11 .
- the partitions 32 g of the premix burner 32 are each formed by a plate in this example, and are arranged in a radial manner when viewed from the combustion chamber 11 . More than one, e.g., two or three, of the fuel nozzles 32 a is provided for each premix chamber 32 f . The fuel injected from each fuel nozzle 32 a is mixed with the compressed air A 2 in the corresponding premix chamber 32 f , and the resulting mixture is ejected into the combustion chamber 11 , i.e., rightward in FIG. 1 .
- FIG. 4 is a sectional view illustrating the structure of a main part of the combustor 2 according to the first embodiment of the present invention, which is a sectional view taken along line IV-IV in FIG. 3 .
- the premixer including the inner cylinder 32 d , the outer cylinder 32 e , and the partitions 32 g is not depicted to avoid complexity in illustration.
- the manifold 40 is a component to distribute the fuel to a plurality of fuel nozzles, which includes at least the premix combustion-use fuel nozzles 32 a to 32 c among the fuel nozzles 31 a and 32 a to 32 c .
- This manifold 40 is housed in a combustor chamber 4 a , see FIG. 1 , of the casing 4 of the gas turbine 100 together with the combustor liner 10 , the outer cylinder 20 of the combustor 2 , and the burner 30 , and is disposed on a central axis C of the combustor liner 10 in the central axis extending direction, i.e., the central axis C passes through the manifold 40 .
- the manifold 40 includes a casing 41 and a plurality of, three in the present embodiment, partitions 42 , 43 , and 44 .
- the casing 41 is a member that forms an exterior of the manifold 40 , and includes a cylindrical outer circumferential face 41 a and an end face 41 b facing the combustion chamber 11 .
- An end opening of the outer circumferential face 41 a on a side on which the combustion chamber 11 lies is closed by the end face 41 b .
- An end of the outer circumferential face 41 a on a side opposite to the side on which the combustion chamber 11 lies is open.
- This casing 41 is, for example, coupled to the outer cylinder 20 of the combustor 2 , so that the manifold 40 is disposed on the central axis C of the combustor liner 10 in the central axis extending direction as mentioned above.
- the premix combustion-use fuel nozzles 32 a to 32 c are provided in large numbers in the end face 41 b of the casing 41 .
- Each of the fuel nozzles 32 a to 32 c defines a hole provided in the end face 41 b in the present embodiment, but may alternatively be formed by a tubular member projecting toward the combustion chamber 11 .
- the end face 41 b is formed by an even flat plate, and each of the fuel nozzles 32 a to 32 c defining a hole open toward the combustion chamber 11 in a direction of the central axis C.
- the combustor 2 is of the multi-stage combustion type, having a plurality of, three in this example, fuel lines, not depicted, and capable of changing the ignition area of the burner in stages, and the premix combustion-use fuel nozzles 32 a are connected to a first fuel line, not depicted. Similarly, the premix combustion-use fuel nozzles 32 b are connected to a second fuel line, not depicted, and the premix combustion-use fuel nozzles 32 c are connected to a third fuel line, not depicted. A separate fuel line is connected to the diffusion combustion-use fuel nozzle 31 a , see FIG. 3 .
- the fuel nozzles 32 a to 32 c are arranged in a ring concealed by the flame stabilizer 33 in FIG. 3 .
- the fuel nozzles 32 b and 32 c are arranged alternately in a circumferential direction with the fuel nozzles 32 a disposed between the fuel nozzles 32 b and 32 c .
- the layout is such that the fuel nozzles 32 a are disposed for one of the premix chambers 32 f , the fuel nozzles 32 b are disposed for one of the premix chambers 32 f adjacent thereto, the fuel nozzles 32 a are disposed for the premix chamber 32 f adjacent thereto, the fuel nozzles 32 c are disposed for the premix chamber 32 f adjacent thereto, and so on. More than one, e.g., two or three, of the fuel nozzles 32 a , 32 b , or 32 c is disposed for each of the premix chambers 32 f.
- the partitions 42 to 44 are members that define a plurality of, or three in this example, annular cavities, or manifold spaces, 45 a , 45 b , and 45 c in the manifold 40 , and are inserted in the casing 41 so as to be arranged in the direction of the central axis C of the combustor liner 10 .
- the partitions 42 to 44 are positioned on the central axis C of the combustor liner 10 and arranged while facing one another in the central axis C direction, and the cavities 45 a to 45 c divided and formed by the partitions 42 to 44 are layered, or superposed one upon another, in the direction of the central axis C inside of the casing 41 .
- a space defined by the end face 41 b and the partition 42 inside of the outer circumferential face 41 a of the casing 41 is the cavity 45 a .
- a space defined by the partitions 42 and 43 inside of the outer circumferential face 41 a of the casing 41 is the cavity 45 b
- a space defined by the partitions 43 and 44 inside of the outer circumferential face 41 a of the casing 41 is the cavity 45 c .
- the number of cavities is three, but the number of cavities may be increased or reduced in accordance with the number of partitions.
- the partition 42 is provided with a plurality of, or the same number as that of premix chambers 32 f for the second fuel line, fuel passages P 1 each in the shape of a straight tube
- the partition 43 is provided with a plurality of, or the same number as that of premix chambers 32 f for the third fuel line, fuel passages P 2 each in the shape of a straight tube.
- Each of the fuel passages P 1 and P 2 is arranged to project toward the combustion chamber 11 .
- the fuel passages P 1 and P 2 are joined to the partitions 42 and 43 , respectively, through welding, for example.
- the partition 44 is not provided with such a fuel passage, and the partition 44 serves as an end wall, or lid, of the casing 41 while defining the cavity 45 c .
- each of the fuel passages which connect one of the cavities to the corresponding fuel nozzles is arranged to pass through another one or more of the cavities to be connected to the corresponding fuel nozzles.
- each fuel passage P 1 passes through the cavity 45 a to connect the cavity 45 b to the corresponding fuel nozzles 32 b .
- each fuel passage P 2 passes through the cavities 45 a and 45 b to connect the cavity 45 c to the corresponding fuel nozzles 32 c .
- the cavity 45 a is directly connected to the fuel nozzles 32 a.
- individual fuel inlets 46 a , 46 b , and 46 c for the cavities 45 a , 45 b , and 45 c , respectively, are provided in the outer circumferential face 41 a of the manifold 40 .
- the first fuel line, the second fuel line, and the third fuel line are connected to the fuel inlet 46 a , the fuel inlet 46 b , and the fuel inlet 46 c , respectively. It is possible to independently control, via each fuel line, the supply and stop of supply of the fuel to the cavities 45 a to 45 c , and to the fuel nozzles 32 a to 32 c.
- the separate fuel line is connected to the fuel nozzle 31 a .
- a fuel pipe, not depicted, connected to the fuel nozzle 31 a is, for example, arranged to pass through a center of the manifold 40 , or inside of the annular cavities 45 a to 45 c , to be connected to the fuel nozzle 31 a.
- manifolds which correspond to the cavities 45 a to 45 c , are generally formed by independent case-like members
- an interior of the casing 41 is divided by the partitions 42 to 44 into the cavities 45 a to 45 c as the manifold spaces arranged in layers. This allows a reduced size of the manifold 40 with improved efficiency in the arrangement of the cavities 45 a to 45 c , or the manifold spaces, and enables the manifold 40 to be included in the combustor 2 and housed in the casing 4 of the gas turbine 100 , i.e., a pressure vessel.
- each of the fuel passages P 1 and P 2 which connects one of the cavities to the corresponding fuel nozzles, passes through another one or more of the cavities, advantageous effects such as an insulation effect for the fuel flowing here, a reduction in a thermal stress due to heat exchange between the fuels, an improvement in heat efficiency due to preheating, and so on can be expected.
- FIG. 5 is a sectional view illustrating the structure of a main part of a combustor according to a second embodiment of the present invention, which corresponds to FIG. 4 .
- elements that are identical or correspond to those in the first embodiment are denoted by the same reference symbols as those in the figures already referred to, and descriptions of such elements are omitted.
- the present embodiment is different from the first embodiment in that fuel passages P 1 and P 2 are arranged to pass through an end face 41 b of a casing 41 , and fuel injection holes 47 are provided in outer circumferential portions of end portions of the fuel passages P 1 and P 2 , which project out of the casing 41 .
- Fuel nozzles 32 b and 32 c are provided in end faces of the fuel passages P 1 and P 2 , respectively.
- the fuel injection holes 47 open for the fuel passages P 1 and P 2 in radial directions of the passages P 1 and P 2 , and a fuel is ejected from each fuel injection hole 47 in a direction perpendicular to a central axis C of a combustor liner 10 .
- the present embodiment is otherwise similar to the first embodiment.
- FIG. 6 is a sectional view illustrating the structure of a main part of a combustor according to a third embodiment of the present invention, which corresponds to FIG. 4 .
- elements that are identical or correspond to those in the first embodiment are denoted by the same reference symbols as those in the figures already referred to, and descriptions of such elements are omitted.
- the present embodiment is different from the first embodiment in that fuel inlets 46 a , 46 b , and 46 c for cavities 45 a , 45 b , and 45 c , respectively, are provided on an end face, or a partition 44 in this example, of a manifold 40 on a side opposite to a side on which a combustion chamber 11 lies.
- the present embodiment is otherwise similar to the first embodiment.
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Abstract
Description
Claims (12)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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JPJP2018-217340 | 2018-11-20 | ||
JP2018217340A JP7489759B2 (en) | 2018-11-20 | 2018-11-20 | Combustor and gas turbine |
JP2018-217340 | 2018-11-20 |
Publications (2)
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US20200158020A1 US20200158020A1 (en) | 2020-05-21 |
US11378276B2 true US11378276B2 (en) | 2022-07-05 |
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US16/686,678 Active 2040-03-24 US11378276B2 (en) | 2018-11-20 | 2019-11-18 | Combustor and gas turbine |
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US (1) | US11378276B2 (en) |
JP (1) | JP7489759B2 (en) |
CN (1) | CN111197766B (en) |
DE (1) | DE102019217830A1 (en) |
Families Citing this family (3)
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CN113654083B (en) * | 2021-08-25 | 2022-06-07 | 西安远航真空钎焊技术有限公司 | Anti-cavity-crossing structure between parallel runners |
KR102583226B1 (en) | 2022-02-07 | 2023-09-25 | 두산에너빌리티 주식회사 | Micromixer with multi-stage fuel supply and gas turbine including same |
KR102583225B1 (en) | 2022-02-07 | 2023-09-25 | 두산에너빌리티 주식회사 | Micromixer and gas turbine comprising the same |
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CN111197766A (en) | 2020-05-26 |
US20200158020A1 (en) | 2020-05-21 |
CN111197766B (en) | 2022-03-08 |
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